24362 Federal Register / Vol. 77, No. 79 / Tuesday, April 24, 2012 / Rules and Regulations 

Aero Seat Service Bulletin 94–25–013, Issue 

4, dated February 12, 2008. 

(1) If no cracking is found on any central 

spreader, repeat the detailed inspection 

thereafter at intervals not to exceed 550 flight 

hours until the replacement specified in 

paragraph (i) of this AD is done. 

(2) If no cracking or only cracks that are 

shorter than 8 mm (0.315 inch) are found on 

any lateral spreader, repeat the detailed 

inspection thereafter at intervals not to 

exceed 550 flight hours until the replacement 

specified in paragraph (i) of this AD is done. 

(3) If all cracks found on any central 

spreader are shorter than 8 mm (0.315 inch), 

before further flight, repair the affected 

spreader, in accordance with paragraphs 2/A 

through C2. of the Accomplishment 

Instructions of Sicma Aero Seat Service 

Bulletin 94–25–011, Revision 3, dated June 

30, 2008. Within 550 flight hours after doing 

the repair, do the detailed inspection 

specified in paragraph (h) of this AD, and 

repeat the inspection thereafter at intervals 

not to exceed 550 flight hours until the 

replacement specified in paragraph (i) of this 

AD is done. 

(4) If one or more cracks are found that are 

8 mm (0.315 inch) or longer on any lateral 

or central spreader, before further flight, 

replace the affected spreader, in accordance 

with paragraphs 2/A through D2. of the 

Accomplishment Instructions of Sicma Aero 

Seat Service Bulletin 94–25–012, Revision 1, 

dated June 26, 2008. 

(i) Optional Terminating Action 

Replacing all central and lateral spreaders 

on an affected seat assembly (modifying to 

‘‘Amendment B’’ standard), in accordance 

with paragraphs 2/A through D2. of the 

Accomplishment Instructions of Sicma Aero 

Seat Service Bulletin 94–25–012, Revision 1, 

dated June 26, 2008, terminates the 

inspections required by this AD for that seat 

assembly. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by this AD, if the actions 

were performed before the effective date of 

this AD using Sicma Aero Seat Service 

Bulletin 94–25–011, Issue 2, dated November 

6, 2007; and Sicma Aero Seat Service 

Bulletin 94–25–012, dated September 25, 

2007. 

(k) Parts Installation 

As of 6 months after the effective date of 

this AD, no person may install any passenger 

seat assembly identified in paragraph (c) of 

this AD, on any airplane, unless it has been 

modified to ‘‘Amendment B’’ standard in 

accordance with the Accomplishment 

Instructions of Sicma Aero Seat Service 

Bulletin 94–25–012, Revision 1, dated June 

26, 2008. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Boston Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the ACO, send it to ATTN: Jeffrey Lee, 

Aerospace Engineer, Boston Aircraft 

Certification Office, FAA, Engine & Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA 01803; telephone (781) 238– 

7161; fax (781) 238–7170; email: 

jeffrey.lee@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(m) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency AD 2008–0097, dated 

May 20, 2008; and the service information 

identified in paragraphs (m)(1), (m)(2), and 

(m)(3) of this AD; for related information. 

(1) Sicma Aero Seat Service Bulletin 94– 

25–011, Revision 3, dated June 30, 2008. 

(2) Sicma Aero Seat Service Bulletin 94– 

25–012, Revision 1, dated June 26, 2008. 

(3) Sicma Aero Seat Service Bulletin 94– 

25–013, Issue 4, dated February 12, 2008. 

(n) Contact Information 

Contact Jeffrey Lee, Aerospace Engineer, 

Boston Aircraft Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone (781) 238–7161; fax (781) 

238–7170; email: jeffrey.lee@faa.gov, for 

more information about this AD. 

(o) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. If you 

accomplish the optional actions specified by 

this AD, you must use the service 

information specified in paragraph (o)(1)(ii) 

of this AD to perform those actions, unless 

the AD specifies otherwise. The Director of 

the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51 on November 21, 

2011 (76 FR 68304, November 4, 2011): 

(i) Sicma Aero Seat Service Bulletin 94– 

25–011, Revision 3, dated June 30, 2008. 

(ii) Sicma Aero Seat Service Bulletin 94– 

25–012, Revision 1, dated June 26, 2008. 

(iii) Sicma Aero Seat Service Bulletin 94– 

25–013, Issue 4, dated February 12, 2008. 

(2) For service information identified in 

this AD, contact Sicma Aero Seat, 7 Rue 

Lucien Coupet, 36100 ISSOUDUN, France, 

telephone: +33 (0) 2 54 03 39 39; fax: +33 (0) 

2 54 03 39 00; email: 

Customerservices.sas@zodiacaerospace.com; 

Internet http:// 

www.sicma.zodiacaerospace.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 9, 

2012. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–9790 Filed 4–23–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1224; Directorate 

Identifier 2011–NM–175–AD; Amendment 

39–17021; AD 2012–08–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD was prompted by 

reports of the air driven generator (ADG) 

failing to power essential buses during 

functional tests, due to the low 

threshold setting of the circuit 

protection on the ADG’s generator 

control unit (GCU) preventing the ADG 

from supplying power to the essential 

buses. This AD requires installing a new 

or serviceable ADG GCU. We are issuing 

this AD to prevent loss of power from 

the ADG to the essential buses which, 

in the event of an emergency, could 

prevent continued safe flight. 

DATES: This AD becomes effective May 

29, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 29, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

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Federal Register / Vol. 77, No. 79 / Tuesday, April 24, 2012 / Rules and Regulations 24363 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Flight Test Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7301; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 8, 2011 (76 FR 

69157). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

There have been several occurrences of the 

air driven generator (ADG) failure to power 

essential buses during functional tests of the 

ADG. It was found that the low threshold 

setting of the circuit protection on the ADG 

generator control unit (GCU) can prevent the 

supply of power from the ADG to the 

essential buses. In the event of an emergency, 

loss of power to the essential buses can 

prevent continued safe flight. 

This [TCCA] directive mandates the 

replacement of the ADG GCU. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Request To Shorten the Compliance 

Time 

The Air Line Pilots Association, 

International (ALPA) requested the 

compliance time of ‘‘24 months after the 

effective date of the AD’’ be reduced 

because ALPA believes that the 

compliance time is too long to comply 

with the proposed AD (76 FR 69157, 

November 8, 2011) based on the 

importance of replacement. 

We do not agree to shorten the 

compliance time. In developing the 

compliance time, we determined that 

the compliance time of 24 months is 

appropriate in considering the safety 

implications, the average utilization rate 

of the affected fleet, the practical aspects 

of an orderly inspection of the fleet 

during regular maintenance periods, 

and the availability of required 

replacement parts. In addition, our 

compliance time corresponds with the 

24-month compliance time of the 

parallel AD issued by Transport Canada 

Civil Aviation (TCCA). We have not 

changed the AD in this regard. 

Request To Reference Hamilton 

Sundstrand’s Part Number 

Comair, Inc. requested that we revise 

paragraphs (g) and (h) of the NPRM (76 

FR 69157, November 8, 2011) to 

reference Hamilton Sundstrand’s part 

number, in addition to the Bombardier 

part numbers for the ADG GCU, because 

by doing so, Comair believes the AD 

will make certain all suspect ADG GCUs 

are removed and replaced and will be 

congruent with the manufacturer’s 

manual. 

We agree with the request to reference 

Hamilton Sundstrand’s part number for 

the ADG GCU that is affected, and not 

higher assembly part numbers. 

Bombardier Service Bulletin 601R–24– 

130, dated April 27, 2011, refers to 

Hamilton Sundstrand Service Bulletin 

ERPS10G–24–1, dated February 9, 2011, 

as an additional source of guidance for 

modifying and testing the ADG GCU 

with new printed wiring assemblies and 

re-identifying the GCU with a new part 

number. We have updated paragraphs 

(g) and (h) of this AD to include the 

Hamilton Sundstrand part number. 

Request To Revise Costs of Compliance 

Section 

Air Wisconsin requested that we 

revise the Costs of Compliance section 

of the NPRM (76 FR 69157, November 

8, 2011) to show a more accurate cost 

to operators of 7 hours labor. While the 

task of replacing the ADG CGU requires 

2 hours of labor, the commenter states 

that post-modification testing requires 

an additional 5 work-hours. 

We partially agree. The work-hours 

quoted in Bombardier Service Bulletin 

601R–24–130, dated April 28, 2011, 

include only the labor time required for 

replacement, while the Hamilton 

Sundstrand service information 

estimates 4 work-hours for replacement 

of the printed wiring assemblies from 

the GCU and functional testing of the 

ADG. Because it may be necessary to do 

a non-destructive test (NDT) inspection 

on some airplanes, we have added an 

additional work-hour. We have changed 

the labor time required to 6 work-hours 

in the Costs of Compliance section of 

this AD. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects 589 

products of U.S. registry. We also 

estimate that it takes 6 work-hours per 

product to comply with the basic 

requirements of this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts cost $0 per product. 

Where the service information lists 

required parts costs that are covered 

under warranty, we have assumed that 

there will be no charge for these parts. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Based on these figures, we estimate the 

cost of the AD on U.S. operators to be 

$300,390, or $510 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

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24364 Federal Register / Vol. 77, No. 79 / Tuesday, April 24, 2012 / Rules and Regulations 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM (76 FR 69157, 

November 8, 2011), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2012–08–04 Bombardier, Inc.: Amendment 

39–17021. Docket No. FAA–2011–1224; 

Directorate Identifier 2011–NM–175–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 29, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes, certificated in any category, serial 

numbers 7305 through 7990 inclusive, and 

8000 through 8109 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24: Electrical Power. 

(e) Reason 

This AD was prompted by reports of the air 

driven generator (ADG) failing to power 

essential buses during functional tests, due to 

the low threshold setting of the circuit 

protection on the ADG’s generator control 

unit (GCU) preventing the ADG from 

supplying power to the essential buses. We 

are issuing this AD to prevent loss of power 

from the ADG to the essential buses which, 

in the event of an emergency, could prevent 

continued safe flight. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Actions 

Within 24 months after the effective date 

of this AD, remove the ADG GCU, 

Bombardier part number (P/N) 604–90800–7 

(Hamilton Sundstrand P/N 761341A), and 

install a new or serviceable ADG GCU, 

Bombardier P/N 604–90800–27 (Hamilton 

Sundstrand 

P/N 761341B), in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–24–130, dated April 

27, 2011. 

(h) Parts Installation 

As of the effective date of this AD, no 

person may install an ADG GCU, Bombardier 

P/N 604–90800–7 (Hamilton Sundstrand P/N 

761341A) on any airplane. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to Attn: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 10, Westbury, New York 11590; 

telephone 516–228–7300; fax 516–794–5531. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2011–26, dated July 25, 2011; 

and Bombardier Service Bulletin 601R–24– 

130, dated April 27, 2011; for related 

information. 

(k) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Bombardier Service Bulletin 601R–24– 

130, dated April 27, 2011. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Issued in Renton, Washington, on April 6, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–9199 Filed 4–23–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1228; Directorate 

Identifier 2011–NM–176–AD; Amendment 

39–17022; AD 2012–08–05] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702), 

CL–600–2D15 (Regional Jet Series 705), 

CL–600–2D24 (Regional Jet Series 900), 

and CL–600–2E25 (Regional Jet Series 

1000) airplanes. This AD was prompted 

by reports of the air driven generator 

(ADG) failing to power essential buses 

during functional tests, due to the low 

threshold setting of the circuit 

protection on the ADG’s generator 

control unit (GCU) preventing the ADG 

from supplying power to the essential 

buses. This AD requires installing a new 

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